Aluminum-zinc-magnesium-copper alloy extrusion

ABSTRACT

An aluminum alloy extrusion product having improved strength and fracture toughness, the aluminum base alloy comprised of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt. % Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidental elements and impurities.

CROSS REFERENCE TO RELATED APPLICATION

[0001] This application claims the benefit of U.S. ProvisionalApplication No. 60/412,200, filed Sep. 21, 2002, incorporated herein byreference.

BACKGROUND OF THE INVENTION

[0002] This invention relates to Al—Zn—Mg—Cu alloys and moreparticularly it relates to Al—Zn—Mg—Cu extrusions and the method ofmaking the same for use in aircraft applications. Further, the inventionrelates to Al—Zn—Mg—Cu alloy extrusion product having improved fracturetoughness.

[0003] Existing Al—Zn—Mg—Cu alloys can have relatively high strengths atmoderate corrosion resistance and moderate damage tolerance or fracturetoughness. Such alloys and methods of obtaining properties are set forthin the patents. For example, U.S. Pat. No. 4,863,528 discloses a methodfor producing an aluminum alloy product and the resulting product havingimproved combinations of strength and corrosion resistance. The methodincludes providing an alloy consisting essentially of about 6-16% zinc,about 1.5-4.5% magnesium, about 1-3% copper, one or more elementsselected from zirconium, chromium, manganese, titanium, vanadium andhafnium, the total of said elements not exceeding about 1%, the balancealuminum and incidental impurities. The alloy is then solution heattreated; precipitation hardened to increase its strength to a levelexceeding the as-solution heat treated strength level by at least about30% of the difference between as-solution heat treated strength and peakstrength; subjected to treatment at a sufficient temperature ortemperatures for improving its corrosion resistance properties; andagain precipitation hardened to raise its yield strength and produce ahigh strength, highly corrosion resistant alloy product.

[0004] U.S. Pat. No. 5,221,377 discloses an alloy product havingimproved combinations of strength, density, toughness and corrosionresistance, said alloy product consisting essentially of about 7.6 to8.4% zinc, about 1.8 to 2.2% magnesium, about 2 to 2.6% copper and atleast one element selected from zirconium, vanadium and hafnium presentin a total amount not exceeding about 0.5%, preferably about 0.05 to0.25% zirconium, the balance aluminum and incidental elements andimpurities. The alloy product, suitable for aerospace applications,exhibits high yield strength, at least about 10% greater yield strengththan its 7X50-T6 counterpart, with good toughness and corrosionresistance properties typically comparable to or better than those ofits 7X50-T76 counterpart. Upper wing members made from this alloytypically have a yield strength over 84 ksi, good fracture toughness andan EXCO exfoliation resistance level of “EC” or better, typically “EB”.

[0005] U.S. Pat. No. 4,477,292 discloses a three-step thermal agingmethod for improving the strength and corrosion resistance of an articlecomprising a solution heat treated aluminum alloy containing zinc,magnesium, copper and at least one element selected from the groupconsisting of chromium, manganese and zirconium. The article isprecipitation hardened at about 175° to 325° F., heat treated for fromseveral minutes to a few hours at a temperature of about 360° to 390° F.and again precipitation hardened at about 175° to 325° F. In a preferredembodiment the article treated comprises aluminum alloy 7075 in the T6condition. The method of the invention is easier to control and issuitable for treating articles of greater thickness than othercomparable methods.

[0006] U.S. Pat. No. 5,108,520 discloses an aging process forsolution-heat-treated, precipitation hardening metal alloy whichincludes first underaging the alloy, such that a yield strength belowpeak yield strength is obtained, followed by higher aging for improvingthe corrosion resistance of the alloy, followed by lower temperatureaging to strength increased over that achieved initially.

[0007] U.S. Pat. No. 5,560,789 discloses AA 7000 series alloys havinghigh mechanical strength and a process for obtaining them. The alloyscontain, by weight, 7 to 13.5% Zn, 1 to 3.8% Mg, 0.6 to 2.7% Cu, 0 to0.5% Mn, 0 to 0.4% Cr, 0 to 0.2% Zr, others up to 0.05% each and 0.15%total, and remainder Al. Either wrought or cast alloys can be obtained,and the specific energy associated with the DEA melting signal of theproduct is lower than 3 J/g.

[0008] U.S. Pat. No. 5,312,498 discloses a method of producing analuminum-based alloy product having improved exfoliation resistance andfracture toughness which comprises providing an aluminum-based alloycomposition consisting essentially of about 5.5-10.0% by weight of zinc,about 1.75-2.6% by weight of magnesium, about 1.8-2.75% by weight ofcopper with the balance aluminum and other elements. The aluminum-basedalloy is worked, heat treated, quenched and aged to produce a producthaving improved corrosion resistance and mechanical properties. Theamounts of zinc, magnesium and copper are stoichiometrically balancedsuch that after precipitation is essentially complete as a result of theaging process, no excess elements are present. The method of producingthe aluminum-based alloy product utilizes either a one- or two-stepaging process in conjunction with the stoichiometrically balancing ofcopper, magnesium and zinc.

[0009] U.S. Pat. No. 4,711,762 discloses an improved aluminum base alloyproduct comprising 0 to 3.0 wt. % Cu, 0 to 1.5 wt. % Mn, 0.1 to 4.0 wt.% Mg, 0.8 to 8.5 wt. % Zn, at least 0.005 wt. % Sr, max. 1.0 wt. % Si,max. 0.8 wt. % Fe and max. 0.45 wt. % Cr, 0 to 0.2 wt. % Zr, theremainder aluminum and incidental elements and impurities.

[0010] U.S. Pat. No. 1,418,303 discloses an improved aluminum alloyconsisting of copper about 0.1% to any amount below 3%, titanium about0.1% to about 2%, zinc about 6% to about 16%, iron (present as animpurity of commercial aluminum) preferably not exceeding 0.6%, silicon(present as an impurity of commercial aluminum) preferably not exceeding0.4%, other elements (impurities) preferably not exceeding 0.4%,remainder aluminum.

[0011] U.S. Pat. No. 2,290,020 discloses an improved aluminum alloyhaving the ternary compound of aluminum, zinc and magnesium present inan amount ranging from about 2% to 20%, the preferred range beingbetween about 3% and 15%. At room temperature the ternary compound goesinto solid solution in aluminum alloys in an amount of about 2%. Thepercentage in solid solution increases at high temperatures anddecreases upon cooling, the excess precipitating out.

[0012] U.S. Pat. No. 3,637,441 discloses an aluminum base powdermetallurgy alloy article having an improved combination ofhigh-transverse yield strength and high-stress corrosion crackingresistance. The alloy contains the basic precipitation hardeningelements zinc, magnesium and copper plus dispersion strengtheningelements iron and nickel. It may additionally contain chromium and/ormanganese. The alloy is prepared by atomization of a melt of theelements, hot-working, solution heat treating, quenching and artificialaging. Components of the alloy in percent by weight are, in addition tothe aluminum, from at least 6.5 to 13 zinc, 1.75 to 6 magnesium, 0.25 to2.5 copper, 0.75 to 4.25 iron and 0.75 to 6 nickel, up to 3 manganeseand up to 0.75 chromium. The iron to nickel ratio is from 0.2:1 to2.0:1.

[0013] U.S. Pat. No. 5,028,393 discloses an Al-based alloy for use assliding material, superior in fatigue resistance and anti-seizureproperty consisting, by weight, of 1-10% Zn, 1-15% Si, 0.1-5% Cu, 0.1-5%Pb, 0.005-0.5% Sr, and the balance Al and incidental impurities.

[0014] U.S. Pat. No. 6,315,842 discloses a mold for plastics made of arolled, extruded or forged AlZnMgCu aluminum alloy product >60 mm thick,and having a composition including, in weight %: 5.7 <Zn<8.7, 1.7<Mg<2.5, 1.2 <Cu<2.2, Fe <0.14, Si<0.11, 0.05 <Zr<0.15, Mn<0.02,Cr<0.02, with Cu+Mg<4.1 and Mg>Cu, other elements <0.05 each and <0.10in total, the product being treated by solution heat treating, quenchingand aging to a T6 temper.

[0015] In spite of these discloses, there is still a great need for animproved alloy and extrusion fabricated therefrom for aerospaceapplications having high levels of strength, corrosion resistance,fracture toughness and good resistance to fatigue crack growth. Thesubject invention provides such an extrusion.

SUMMARY OF THE INVENTION

[0016] It is an object of the invention to provide an improvedAl—Zn—Mg—Cu alloy extrusion for use in aircrafts.

[0017] It is another object of the invention to provide an Al—Zn—Mg—Cualloy extrusion having improved fracture toughness as well as havinghigh strength levels.

[0018] It is yet another object of the invention to provide a method forproducing an Al—Zn—Mg—Cu alloy extrusion having improved strengthproperties, fracture toughness and resistance to fatigue crack growth.

[0019] It is still another object of the invention to provide a methodfor producing an Al—Zn—Mg—Cu alloy product having improved strengthproperties, fracture toughness, good levels of corrosion resistance.

[0020] It is another object of this invention to provide aerospacestructural members such as extrusions from the alloy of the invention.

[0021] In accordance with these objects, there is provided a method ofproducing an aluminum alloy extrusion product having improved fracturetoughness, the method comprising the steps of providing a molten body ofan aluminum base alloy comprised of 1.95 to 2.5 wt. % Cu, 1.9 to 2:5 wt.% Mg, 8.2 to 10 wt. % Zn, 0.05 to 0.25 wt. % Zr, max.

[0022] 0.15 wt. % Si, max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, theremainder aluminum and incidental elements and impurities; and castingthe molten body of the aluminum base alloy to provide a solidified body,the molten aluminum base alloy being solidified at a rate betweenliquidus and solidus temperatures in the range of 600° to 800° K. persecond to provide a solidified body having a grain size in the range of25 to 75 μm. Thereafter, the body is homogenized by heating in a firsttemperature range of 840° to 860° F. followed by heating in a secondtemperature range of 680° to 880° F. to provide a homogenized bodyhaving a uniform distribution of MgZn₂ or η precipitate. The homogenizedbody is then extruded to provide an extrusion, the extruding beingcarried out in a temperature range of 600° to 850° F. and at a ratesufficient to maintain at least 80% of said extrusion in anon-recrystallized condition. The extrusion is solution heat treated andartificial aged to improve strength properties and to provide anextrusion product having improved fracture toughness.

[0023] The improved aluminum base alloy extrusion product can have afracture toughness of 8% or greater and a yield strength of 3% orgreater than a similarly sized 7xxx product.

[0024] The invention also includes an improved aluminum base alloywrought product such as an extrusion product consisting essentially of1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt. % Zn, 0.05 to0.25 wt. % Zr, 0.05 to 0.2 wt. % Sc, max. 0.15 wt. % Si, max. 0.15 wt. %Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidental elementsand impurities.

BRIEF DESCRIPTION OF THE DRAWINGS

[0025]FIG. 1 is a flow chart showing steps of the invention.

[0026]FIG. 2 illustrates the results of the damage tolerance (normalizeddenting speed) of the invention alloy (M703) compared to a high strength7xxx alloys (SSLLC).

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

[0027] Referring to FIG. 1, there is shown a flow chart of steps in theinvention. Generally, in the steps a molten body of Al—Zn—Mg—Cu alloy iscast at a controlled solidification rate to obtain a specific grain sizerange in the cast body. Thereafter, the cast body is homogenized undercontrolled conditions to obtain a uniform distribution of MgZn₂ or ηprecipitate. The body is extruded in a specific rate range andtemperature to obtain an extrusion having a large portion thereof, e.g.,at least 80%, in a non-recrystallized condition. The extrusion is thensolution heat treated and aged to very high levels of strength, fracturetoughness and corrosion resistance.

[0028] The alloy of the invention contains about 8.2 to 10 wt. % Zn, 1.9to 2.5 wt. % Mg, 1.95 to 2.5 wt. % Cu, 0.05 to 0.25 wt. % Zr, max. 0.15wt. % Si, max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum,incidental elements and impurities.

[0029] Preferably, the alloy contains 1.95 to 2.3 wt. % Cu, 1.9 to 2.3wt. % Mg,

[0030] 8.45 to 9.4 wt. % Zn, 0.05 to 0.2 wt. % Cr and 0.05 to 0.15 wt. %Zr. Cr can range from 0.05 to 0.08 wt. %. For purposes of retardingrecrystallization, the alloys can contain 0.01 to 0.2 wt. % Sc,preferably 0.01 to 0.1 wt. %. Such alloys when processed in accordancewith the invention possess marked improvements in fracture toughness atacceptable or even high levels of strength and corrosion resistancecompared to conventional 7xxx alloys such as AA7075-T6, for example. Thecomposition of the AA 7xxx alloys are set forth in The AluminumAssociation publication entitled “Registration Record of AluminumAssociation Designations and Chemical Composition Limits for WroughtAluminum and Wrought Aluminum Alloys”, dated December 1993. The term“7xxx” means aluminum alloys containing zinc as a main alloyingingredient. AA 7075-T6 refers to AA compositional limits as registeredwith The Aluminum Association. A typical T6 aging practice for 7075 isheating at about 250° F. for 24 hours and a typical temperature range isabout 175° to 330° F. for 3 to 30 hours.

[0031] For purposes of the present invention, a molten aluminum alloy ofthe invention is cast into a solidified body at a rate which provides acontrolled microstructure or grain size. Such molten aluminum alloytypically is cast in the form of billet when it is desired to produceextrusion products. Further, typically such solidified body is cast at arate of about 1 to 6 inches per minute, preferably 2 to 4 inches perminute, and typically the billet has a diameter in the range of about 1to 7 inches. For purposes of the invention, it is preferred that thesolidified body has an average grain size in the range of 25 to 100 μm,preferably 35 to 75 μm. If the alloy of the invention is cast atcontrolled rates and thermally mechanically processed in accordance withthe invention, very high tensile and compressive strengths, fracturetoughness and corrosion resistance can be obtained. That is, forpurposes of obtaining the desired microstructure for thermal mechanicalprocessing in accordance with the invention, the molten aluminum is castat a controlled solidification rate. It has been discovered thatcontrolled solidification rate of the disclosed aluminum alloy incombination with subsequent controlled thermal mechanical processingresults in extruded products having superior properties, i.e., very hightensile strength, good corrosion and dent resistance.

[0032] It should be noted that the strength of the subject aluminumalloys can be improved by dispersion hardening or by strain hardening.Strain hardening is the result of plastic deformation and is dependenton the degree of deformation. Dispersion hardening is produced throughformation of clusters of atoms (referred to as Guiner-Preston or GPzones). In addition, dispersion hardening can result from the formationof new phases or precipitates in the alloy which form barriers againstdislocation movement. This can significantly increase the strength ofthe alloy. In the Al—Zn—Mg—Cu alloys, new strengthening phases includeMgZn₂, also known as M or η-phase; Mg₃Zn₃Al₂ also as the T-phase;CuMgAl₂ also known as the S-phase. Strengthening resulting fromprecipitation of new phases is more effective than strengthening byformation of GP zones. However, strengthening by precipitation of newphases can have an adverse effect on damage tolerance or fracturetoughness. Usually, the greater the volume fraction in the precipitationphases, the lower is the damage tolerance. By comparison, strengtheningresulting from GP zone formation does not take place at the expense ofdamage tolerance. Thus, to provide for improved strength and damagetolerance, the present invention balances the volume fraction ofprecipitates and the volume fraction of GP zones or zinc-rich clustersin the final product while maintaining excess zinc in solution. For thepurpose of the invention the GP zones size should be in the range of 2to 35 nm and the GP zones density should be in the range of 4×10¹⁸ to5×10¹⁸ zones per cm³.

[0033] For purposes of producing billet in accordance with theinvention, casting may be accomplished using a mold cooled by an air andliquid coolant to solidify billet at a controlled rate which providesthe desired grain size or structure. The grain can have a size in therange of 35 to 75 μm. The air and coolant mixture used with the moldsare particularly suited for extracting heat from the body of moltenaluminum alloy to obtain a solidification rate of 5° to 50° C. persecond for billet having a diameter of 1 to 6 inches. Molds using theair and coolant mixture which are suitable for controlling the coolingrate for casting molten aluminum alloy of the invention are described inU.S. Pat. No. 4,598,763. The coolant for use with these molds for theinvention is comprised of a gas and a liquid where gas is infused intothe liquid as tiny, discrete undissolved bubbles and the combination isdirected on the surface of the emerging ingot. The bubble-entrainedcoolant operates to cool the metal at an increased rate of heatextraction; and if desired, the increased rate of extraction, togetherwith the discharge rate of the coolant, can be used to control the rateof cooling at any stage in the casting operation, including during thesteady state casting stage.

[0034] For casting metal, e.g., aluminum alloy to provide amicrostructure suitable for purposes of the present invention, moltenmetal is introduced to the cavity of an annular mold, through one endopening thereof, and while the metal undergoes partial solidification inthe mold to form a body of the same on a support adjacent the other endopening of the cavity, the mold and support are reciprocated in relationto one another endwise of the cavity to elongate the body of metalthrough the latter opening of the cavity. Liquid coolant is introducedto an annular flow passage which is circumposed about the cavity in thebody of the mold and opens into the ambient atmosphere of the moldadjacent the aforesaid opposite end opening thereof to discharge thecoolant as a curtain of the same that impinges on the emerging body ofmetal for direct cooling. Meanwhile, a gas which is substantiallyinsoluble in the coolant liquid is charged under pressure into anannular distribution chamber which is disposed about the passage in thebody of the mold and opens into the passage through an annular slotdisposed upstream from the discharge opening of the passage at theperiphery of the coolant flow therein. The body of gas in the chamber isreleased into the passage through the slot and is subdivided into amultiplicity of gas jets as the gas discharges through the slot. Thejets are released into the coolant flow at a temperature and pressure atwhich the gas is entrained in the flow as a mass of bubbles that tend toremain discrete and undissolved in the coolant as the curtain of thesame discharges through the opening of the passage and impinges on theemerging body of metal. With the mass of bubbles entrained therein, thecurtain has an increased velocity, and this increase can be used toregulate the cooling rate of the coolant liquid, since it more thanoffsets any reduction in the thermal conductivity of the coolant. Infact, the high velocity bubble-entrained curtain of coolant appears tohave a scrubbing effect on the metal, which breaks up any film andreduces the tendency for film boiling to occur at the surface of themetal, thus allowing the process to operate at the more desirable levelof nucleate boiling, if desired. The addition of the bubbles alsoproduces more coolant vapor in the curtain of coolant, and the addedvapor tends to rise up into the gap normally formed between the body ofmetal and the wall of the mold immediately above the curtain to cool themetal at that level. As a result, the metal tends to solidify further upthe wall than otherwise expected, not only as a result of the highercooling rate achieved in the manner described above, but also as aresult of the build-up of coolant vapor in the gap. The higher levelassures that the metal will solidify on the wall of the mold at a levelwhere lubricating oil is present; and together, all of these effectsproduce a superior, more satin-like, drag-free surface on the body ofthe metal over the entire length of the ingot and is particularly suitedto thermal transformation.

[0035] When the coolant is employed in conjunction with the apparatusand technique described in U.S. Pat. No. 4,598,763, this casting methodhas the further advantage that any gas and/or vapor released into thegap from the curtain intermixes with the annulus of fluid dischargedfrom the cavity of the mold and produces a more steady flow of thelatter discharge, rather than the discharge occurring as intermittentpulses of fluid.

[0036] As indicated, the gas should have a low solubility in the liquid;and where the liquid is water, the gas may be air for cheapness andready availability.

[0037] During the casting operation, the body of gas in the distributionchamber may be released into the coolant flow passage through the slotduring both the butt forming stage and the steady state casting stage.Or, the body of gas may be released into the passage through the slotonly during the steady state casting stage. For example, during thebutt-forming stage, the coolant discharge rate may be adjusted toundercool the ingot by generating a film boiling effect; and the body ofgas may be released into the passage through the slot when thetemperature of the metal reaches a level at which the cooling raterequires increasing to maintain a desired surface temperature on themetal. Then, when the surface temperature falls below the foregoinglevel, the body of gas may no longer be released through the slot intothe passage, so as to undercool the metal once again. Ultimately, whensteady state casting is begun, the body of gas may be released into thepassage once again, through the slot and on an indefinite basis untilthe casting operation is completed. In the alternative, the coolantdischarge rate may be adjusted during the butt-forming stage to maintainthe temperature of the metal within a prescribed range, and the body ofgas may not be released into the passage through the slot until thecoolant discharge rate is increased and the steady state casting stageis begun.

[0038] The coolant, molds and casting method are further set forth inU.S. Pat. Nos. 4,598,763 and 4,693,298, incorporated herein byreference.

[0039] While the casting procedure for the present invention has beendescribed in detail for producing billet having the necessary structurefor thermal transformation in accordance with the present invention, itshould be understood that the other casting methods can be used toprovide the solidification rates that result in the grain structurenecessary to the invention. As noted earlier, such solidification can beobtained by belt, block or roll casting and electromagnetic casting.

[0040] A seven inch billet of an alloy containing 8.9 wt. % Zn, 2.1 wt.% Mg, 2.3 wt. % Cu, 0.11 wt. % Zr, the remainder comprising aluminum,cast employing a mold using air and water coolant, at a cooling rate of35° to 50° F. per second provides a satisfactory grain structure forextruding and thermally mechanically processing in accordance with theinvention.

[0041] While casting has been described with respect to billet, it willbe appreciated that the principles described herein may be applied toingot or electromagnetic casting of the aluminum alloys.

[0042] After the billet is cast, it is subjected to a homogenizationtreatment. Preferably, the billet is subjected to two homogenizationtreatments. In the first homogenization treatment, the billet preferablyis treated in a temperature range of 840° to 880° F. for a period of 6to 18 hours. Thereafter, the billet is then preferably subjected to atemperature range of 880° to 900° F. for a period of 4 to 36 hours.Subjecting the billet to a double homogenization treatment as describedprovides a billet with a more uniform distribution of MgZn₂ precipitateor M or η-phase as well as zinc and chromium containing dispersoids.

[0043] After homogenization, the billet is extruded to provide anextrusion member. For purposes of extruding, the billet is heated to atemperature range of 600° to 850° F. and maintained in this temperaturerange during extruding. Preferably, the billet is extruded at a rate inthe range of 0.8 to 8 ft/min and preferably at an extrusion ratio in therange of 10 to 60. These conditions are important to obtain an extrusionwherein at least 80% and preferably 90% of the extrusion is maintainedin the unrecrystallized condition. The extrusion can have an aspectratio between the thinnest and thickest section of 1:4 to 1:18.

[0044] After extruding, the product is solution heat treated by heatingin a temperature range of about 845° F. to about 900° F., with apreferred temperature range being 870° to 890° F. Typical times at thesetemperatures can range from 5 to 120 minutes. The solution heat treatingshould be carried out for a time sufficient to dissolve a substantialportion of the alloying elements. That is, substantially all of thezinc, magnesium and copper is dissolved to provide a solid solution.

[0045] After solution heat treating, the extrusion is rapidly cooled orquenched by immersion or spraying with cold water, for example. Afterquenching, the extrusion may be straightened and/or stretched. That is,the extrusion is straightened prior to aging to improve strengthproperties.

[0046] After solution heat treating, the extrusion is treated to improveproperties such as strength, corrosion and fracture toughness.

[0047] Thus, the extrusion may be subject to different thermaltreatments depending on the properties desired. For example, theextrusion may be subject to a single step thermal treatment to achievehigh or peak strength, referred to as T6 type tempers. However, suchtempers can be susceptible to stress corrosion cracking. T6 tempers areobtained by aging at a temperature range of 175° to 325° F. for 3 to 30hours. A two step aging process may be employed wherein a first agingstep is carried out at 175° to 300° F. for a period of time of 3 to 30hours, followed by a second aging step carried out at 300° to 360° F.for a period of time of 3 to 24 hours. This aging process produces anoveraged temper referred as T7x temper. This condition improves stresscorrosion cracking but can decrease strength.

[0048] To improve strength and corrosion resistance, the extrusion maybe subject to a three-step aging process. The aging steps or phasesinclude a low-high-low aging sequence. In the first or low aging step,the extrusion is subject to a temperature for a period of time whichprecipitation hardens the extrusion to a point at or near peak strength.This can be effected by subjecting the extrusion to precipitationhardening in a temperature range of about 150° to 325° F. typically fora time between 2 to 30 hours. Then, the extrusion is subject to a secondtreatment to improve corrosion resistance. The second treatment includessubjecting the extrusion to a temperature range of 300° to 500° F. for 5minutes to about 3 hours, for example. In the third step, the extrusionis subject to another strengthening step. The third thermal treatmentincludes subjecting the extrusion to a temperature of 175° to 325° F.for about 2 to 30 hours.

[0049] Exfoliation corrosion (EXCO) behavior of the inventive alloy wascompared to 7075 T6511 and 7075 T76511 alloys. The American Society forTesting and Materials developed a method (ASTM G34-99) that provides anaccelerated exfoliation corrosion test for 2xxx and 7xxx series aluminumalloys. The susceptibility to exfoliation is determined by visualexamination, with performance ratings established by reference tostandard photographs. When tested in accordance with this test methodthe alloy of the invention exhibits a typical EA exfoliation corrosionrating when aged to a T76 temper. When aged to a T77 temper theinvention alloy exhibits a typical EB exfoliation corrosion rating.

[0050] While alloy has been described with respect to extrusionproducts, it can find use as sheet and plate product and such iscontemplated herein.

[0051] All ranges set forth herein include all the numbers within therange as if specifically set forth.

[0052] The products or members described herein in accordance with theinvention are particularly suitable for aerospace applications and findsmany uses in large aircrafts such as commercial and military aircrafts.The products can be used in wing components, tail assemblies, fuselagesections or in subassemblies or other components comprising theaircraft. That is, the aircraft assemblies can comprise a wing assemblyor wing subassembly, a center wing box assembly or subassembly, floorassembly or subassembly including seat tracks, floor beams, stanchions,cargo deck assemblies and subassemblies, floor panels, cargo floorpanels, fuselage assemblies or subassemblies, fuselage frames, fuselagestringers and the like. Further, the products may be produced asseamless or non-seamless tubes and used in sporting goods such asbaseball bats. TABLE Typical mechanical properties of the inventivealloy (M703) in comparison to 7075 T6511 and 7150 T77511 for extrusions0.249 inch thick Alloy Temper UTS, ksi YS, ksi e, % K_(Ic) 7075 T6511 8882 10 28 M703 T76511 97 93 10 33 M703 T77511 102 100 9 32.5 7150 T7751193 89 9 27

[0053] The table illustrates the mechanical properties of the inventivealloy when aged to a T76 and a T77 tempers.

[0054] The following examples are still further illustrative of theinvention.

EXAMPLE 1

[0055] A billet of an alloy containing 8.9 wt. % Zn, 2.1 wt. % Mg, 2.3wt. % Cu, 0.11 wt. % Zr, incidental elements and impurities, the balancealuminum, was cast into a seven inch diameter billet. The billet wascast using casting molds utilizing air and liquid coolant (availablefrom Wagstaff Engineering, Inc., Spokane, Wash.). The air/water coolantwas adjusted in order that the body of molten aluminum alloy was cast ata rate of 4 inches per minute. The as-cast structure had an averagegrain size of 35 μm. The billet was homogenized for 8 hours at 870° F.and then for 24 hours at 890° F. Thereafter, the billet was brought to atemperature of 725° F. and extruded into a hollow tube with an outsidediameter of 2.65 inch and a wall thickness of 0.080 inch.

[0056] The extrusion had a non-recrystallized grain structure. Theextrusion was solution heat treated for 25 minutes at 880° F. andquenched in a water-15% glycol solution. Thereafter, the quenchedextrusion was precipitation hardened for 24 hours at 250° F. and thensubjected to a temperature of 31 5° F. for 6 hours to improve corrosionresistance and yield strength properties. The extrusion was then testedfor tensile strength and yield strength and compared to AA 7075 T6. Theresults are reproduced in Table 1.

[0057] The extrusion was then tested for dent resistance or damagetolerance. The dent resistance test was performed by pitching balls ofconstant size and weight at the extruded tube. The number of pitches tothe first dent on the extrude tube represents the dent resistance. Theextrusion was compared to a AA 7055 alloy treated in a similar fashion.The alloy of the invention is referred to as M703 and 7055 as SSLLC (seeFIG. 2). Both alloys were aged identically. It will be seen from FIG. 2that M703 had superior dent resistance.

EXAMPLE 2

[0058] A billet of an alloy containing 8.9 wt. % Zn, 2.1 wt. % Mg, 2.3wt. % Cu, 0.11 wt. % Zr, incidental elements and impurities, the balancealuminum, was cast into a seven inch diameter billet. The billet wascast using casting molds utilizing air and liquid coolant (availablefrom Wagstaff Engineering, Inc., Spokane, Wash.). The air/water coolantwas adjusted in order that the body of molten aluminum alloy was cast ata rate of 4 inches per minute. The as-cast structure had an averagegrain size of 35 μm. The billet was homogenized for 8 hours at 870° F.and then for 24 hours at 890° F. Thereafter, the billet was brought to atemperature of 725° F. and extruded into an aircraft stringer having a“T” shaped cross section and a wall thickness of 0.245 inches.

[0059] The extrusion had a non-recrystallized grain structure. Theextrusion was solution heat treated for 35 minutes at 880° F. andquenched in a water-15% glycol solution. Thereafter, the quenchedextrusion was precipitation hardened for 24 hours at 250° F. followed by25 to 35 minutes at 380° F., then subjected to a temperature of 250° F.for 24 hours. The extrusion was then tested for tensile strength andyield strength and fracture toughness, fatigue crack growth and comparedto AA 7075 T6511 and AA 7150 T775 11. The results are reproduced inTable 1. It will be seen that the inventive alloy has superior strengthand fracture toughness when compared to AA 7075 T6511 and AA 7150T77511. Also, the extrusion has a unique combination of tensilestrength, corrosion resistance, and damage tolerance (i.e., fracturetoughness and fatigue crack growth).

[0060] Having described the presently preferred embodiments, it is to beunderstood that the invention may be otherwise embodied within the scopeof the appended claims.

What is claimed is:
 1. A method of producing an aluminum alloy extrusionproduct having improved fracture toughness, the method comprising thesteps of: (a) providing a molten body of an aluminum base alloycomprised of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt. %Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max. 0.15 wt. % Fe, max.0.1 wt. % Mn, the remainder aluminum and incidental elements andimpurities; (b) casting said molten body of said aluminum base alloy toprovide a solidified body, said molten aluminum base alloy being cast ata rate in the range of 1 to 6 inches per minute; (c) homogenizing saidbody by heating in a first temperature range of 840 to 860° F. followedby heating in a second temperature range of 860° to 880° F. to provide ahomogenized body having a uniform distribution of η precipitate andzirconium containing dispersoids; (d) extruding said homogenized body toprovide an extrusion, said extruding being carried out in a temperaturerange of 6000° to 850° F. and at a rate sufficient to maintain at least80% of the cross-sectional area of said extrusion in anon-recrystallized condition; (e) solution heat treating said extrusion;and (f) artificial aging said product to improve strength properties toprovide an extrusion product having improved fracture toughness.
 2. Themethod in accordance with claim 1 wherein the alloy contains 1.95 to 2.3wt. % Cu.
 3. The method in accordance with claim 1 wherein the alloycontains 1.9 to 2.3 wt. % Mg.
 4. The method in accordance with claim 1wherein the alloy contains 0.05 to 0.2 wt. % Cr.
 5. The method inaccordance with claim 1 wherein the alloy contains 8.45 to 9.4 wt. % Zn.6. The method in accordance with claim 1 wherein the alloy contains 0.01to 0.1 wt. % Sc.
 7. The method in accordance with claim 1 wherein thealloy contains 0.01 to 0.2 wt. % Ti.
 8. The method in accordance withclaim 1 including heating in said first temperature range for 6 to 18hours.
 9. The method in accordance with claim 1 including heating insaid second temperature range for 4 to 36 hours.
 10. The method inaccordance with claim 1 including rapidly quenching said extrusion. 11.The method in accordance with claim 1 wherein said extruding is carriedout at a rate in the range of 0.5 to 8 ft/min.
 12. The method inaccordance with claim 1 wherein said solution heat treating is carriedout in a temperature range of 870° to 890° F. for 5 to 120 minutes. 13.The method in accordance with claim 1 wherein said artificial aging iscarried out by aging in a temperature range of 175° to 300° F. for 3 to30 hours followed by aging at 280° to 360° F. for 3 to 24 hours.
 14. Themethod in accordance with claim 1 wherein said artificial aging iscarried out by aging in a temperature range of 210° to 280° F. for 4 to24 hours followed by aging at 320° to 400° F. for 30 minutes to 14hours.
 15. The method in accordance with claim 1 wherein said artificialaging is carried out by aging in a temperature range of 150° to 325° F.for 2 to 30 hours followed by aging at 300° to 500° F. for 5 minutes to3 hours followed by aging at 175° to 325° F. for 2 to 30 hours.
 16. Themethod in accordance with claim 1 wherein said artificial aging is athree-step process wherein said first and third steps improve strengthand a second step improves corrosion resistance.
 17. The method inaccordance with claim 1 wherein said artificial aging includes aging:(i) at a low temperature above room temperature to precipitation hardensaid extrusion; (ii) at temperatures to improve corrosion resistanceproperties of said extrusion; and (iii) at lower temperatures above roomtemperature to precipitation harden said extrusion.
 18. The method inaccordance with claim 1 wherein the extrusion has a fracture toughnessat least 5% greater than a similar extrusion fabricated from 7075 alloy.19. The method in accordance with claim 1 wherein the extrusion has atensile strength at least 8% greater than a similar extrusion fabricatedfrom 7075 alloy.
 20. A method of producing an aluminum alloy extrusionproduct having improved strength and fracture toughness, the methodcomprising the steps of: (a) providing a molten body of an aluminum basealloy comprised of 1.95 to 2.3 wt. % Cu, 1.9 to 2.3 wt. % Mg, 8.2 to 9.4wt. % Zn, 0.05 to 0.2 wt. % Cr, 0.05 to 0.15 wt. % Zr, max. 0.15 wt. %Si, max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum andincidental elements and impurities; (b) casting said molten body of saidaluminum base alloy to provide a solidified body, said molten aluminumbase alloy being cast at a rate in the range of 1 to 6 inches perminute; (c) homogenizing said body by heating in a first temperaturerange of 840° to 860° F. for 6 to 24 hours followed by heating in asecond temperature range of 860° to 880° F. for 4 to 36 hours to providea homogenized body having a uniform distribution of η precipitate andzirconium and chromium containing dispersoids; (d) extruding saidhomogenized body to provide an extrusion, said extruding being carriedout in a temperature range of 600° to 850° F. and at a rate in the rangeof 0.5 to 8.0 ft/min to provide an extrusion with the non-recrystallizedarea representing at least 80% of the cross sectional area of theextrusion; (e) rapidly quenching said extrusion; (f) solution heattreating said extrusion; and (g) artificial aging said product toimprove strength properties to provide an extrusion product havingimproved fracture toughness.
 21. The method in accordance with claim 20wherein the alloy contains 0.01 to 0.1 wt. % Sc.
 22. The method inaccordance with claim 20 wherein the alloy contains 0.01 to 0.2 wt. %Ti.
 23. The method in accordance with claim 20 wherein said solutionheat treating is carried out in a temperature range of 870° to 890° F.for 5 to 120 minutes.
 24. The method in accordance with claim 20 whereinsaid artificial aging is carried out by aging in a temperature range of175° to 300° F. for 3 to 30 hours followed by aging at 280° to 360° F.for 3 to 24 hours.
 25. The method in accordance with claim 20 whereinsaid artificial aging is carried out by aging in a temperature range of245° to 255° F. for 6 to 24 hours followed by aging at 360° to 390° F.for 5 to 120 minutes.
 26. The method in accordance with claim 20 whereinsaid artificial aging is a three-step process wherein said first andthird steps improve strength and a second step improves corrosionresistance.
 27. The method in accordance with claim 20 wherein saidartificial aging includes aging: (i) at a low temperature above roomtemperature to precipitation harden said extrusion; (ii) at temperaturesto improve corrosion resistance properties of said extrusion; and (iii)at lower temperatures above room temperature to precipitation hardensaid extrusion.
 28. The method in accordance with claim 20 wherein theextrusion has a fracture toughness at least 5% greater than a similarextrusion fabricated from 7075 alloy.
 29. The method in accordance withclaim 20 wherein said artificial aging is carried out by aging in atemperature range of 150° to 325° F. for 2 to 30 hours followed by agingat 300° to 500° F. for 5 minutes to 3 hours followed by aging at 175° to325° F. for 2 to 30 hours.
 30. A method of producing an aluminum alloyextrusion product having improved strength and fracture toughness, themethod comprising the steps of: (a) providing a molten body of analuminum base alloy comprised of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. %Mg, 8.2 to 10 wt. % Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max.0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidentalelements and impurities; (b) casting said molten body of said aluminumbase alloy to provide a solidified body, said molten aluminum base alloybeing cast at a rate in the range of 1 to 4 inches per minute; (c)homogenizing said body to provide a homogenized body having a uniformdistribution of η precipitate; (d) extruding said homogenized body toprovide an extrusion, said extruding being carried out in a temperaturerange of 600° to 850° F. at an extrusion ratio in the range of 10 to 60and an extrusion rate in the range of 0.5 to 8.0 ft/min to provide saidextrusion in a substantially non-recrystallized condition; (e) rapidlyquenching said extrusion; (f) solution heat treating said extrusion; and(g) artificial aging said product to improve strength properties toprovide an extrusion product having improved fracture toughness.
 31. Themethod in accordance with claim 30 wherein the alloy contains 0.05 to0.2 wt. % Cr.
 32. The method in accordance with claim 30 wherein thealloy contains 0.01 to 0.2 wt. % Ti.
 33. The method in accordance withclaim 30 wherein the alloy contains 0.01 to 0.2 wt. % Sc.
 34. The methodin accordance with claim 30 wherein said solution heat treating iscarried out in a temperature range of 875° to 885° F. for 5 to 120minutes.
 35. The method in accordance with claim 30 wherein saidartificial aging is carried out by aging in a temperature range of 175°to 300° F. for 3 to 30 hours followed by aging at 280° to 360° F. for 3to 24 hours.
 36. The method in accordance with claim 30 wherein saidartificial aging is carried out by aging in a temperature range of 210°to 280° F. for 4 to 24 hours followed by aging at 300° to 400° F. for 1to 14 hours.
 37. The method in accordance with claim 30 wherein saidartificial aging includes aging: (i) at a low temperature above roomtemperature to precipitation harden said extrusion; (ii) at temperaturesto improve corrosion resistance properties of said extrusion; and (iii)at lower temperatures above room temperature to precipitation hardensaid extrusion.
 38. The method in accordance with claim 30 wherein saidartificial aging is carried out by aging in a temperature range of 150°to 325° F. for 2 to 30 hours followed by aging at 300° to 500° F. for 5minutes to 3 hours followed by aging at 175° to 325° F. for 2 to 30hours.
 39. An improved aluminum base alloy wrought product consistingessentially of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt.% Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max. 0.15 wt. % Fe,max. 0.1 wt. % Mn, the remainder aluminum and incidental elements andimpurities, said alloy product having a fracture toughness of 5% orgreater and a yield strength of 8% or greater than a similarly sized7075 product.
 40. The alloy product in accordance with claim 39 whereinthe alloy contains 1.95 to 2.3 wt. % Cu.
 41. The alloy product inaccordance with claim 39 wherein the alloy contains 1.9 to 2.3 wt. % Mg.42. The alloy product in accordance with claim 39 wherein the alloycontains 0.05 to 0.2 wt. % Cr.
 43. The alloy product in accordance withclaim 39 wherein the alloy contains 8.45 to 9.4 wt. % Zn.
 44. The alloyproduct in accordance with claim 39 wherein the alloy contains 0.01 to0.2 wt. % Sc.
 45. The alloy product in accordance with claim 39 whereinthe alloy contains 0.01 to 0.2 wt. % Ti.
 46. The alloy product inaccordance with claim 39 wherein said product is an extrusion product.47. The alloy product in accordance with claim 39 wherein the alloyproduct is an extrusion having an aspect ratio between the thinnest andthe thickest section of 1:4 to 1:18.
 48. The alloy product in accordancewith claim 39 wherein said product is an aircraft stringer.
 49. Thealloy product in accordance with claim 39 wherein said product is anaircraft floor beam.
 50. The alloy product in accordance with claim 39wherein said product is an aircraft fuselage beam.
 51. The alloy productin accordance with claim 39 wherein said product is a hollow extrudedproduct.
 52. The alloy product in accordance with claim 39 wherein saidproduct is a hollow non-seamless extruded product.
 53. The alloy productin accordance with claim 39 wherein said product is a hollow seamlessextruded product.
 54. The alloy product in accordance with claim 39wherein said product is a baseball bat.
 55. The alloy product inaccordance with claim 39 wherein said product is an automobile rockerarm.
 56. An improved aluminum base alloy wrought product consistingessentially of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt.% Zn, 0.05 to 0.25 wt. % Zr, 0.05 to 0.2 wt. % Sc, max 0.15 wt. % Si,max. 0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum andincidental elements and impurities.
 57. The alloy product in accordancewith claim 56 wherein the alloy contains 0.05 to 0.2 wt. % Cr.
 58. Thealloy product in accordance with claim 56 wherein the alloy contains0.05 to 0.2 wt. % Ti.
 59. An improved aluminum base alloy wroughtproduct consisting essentially of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. %Mg, 8.2 to 10 wt. % Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max.0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidentalelements and impurities, said alloy product having a fracture toughnessof 5% or greater, a yield strength of 8% or greater than a similarlysized 7075 product and having an exfoliation resistance of EB or better.60. An improved aluminum base alloy aircraft member consistingessentially of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. % Mg, 8.2 to 10 wt.% Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max. 0.15 wt. % Fe,max. 0.1 wt. % Mn, the remainder aluminum and incidental elements andimpurities, said alloy product having a fracture toughness of 5% orgreater and a yield strength of 8% or greater than a similarly sized7075 product.
 61. The alloy product in accordance with claim 60 whereinsaid member is an aircraft stringer.
 62. The alloy product in accordancewith claim 60 wherein said member is an aircraft floor beam.
 63. Thealloy product in accordance with claim 60 wherein said member is anaircraft fuselage beam.
 64. An improved aluminum base alloy aircraftmember consisting essentially of 1.95 to 2.5 wt. % Cu, 1.9 to 2.5 wt. %Mg, 8.2 to 10 wt. % Zn, 0.05 to 0.25 wt. % Zr, max. 0.15 wt. % Si, max.0.15 wt. % Fe, max. 0.1 wt. % Mn, the remainder aluminum and incidentalelements and impurities, said alloy product having a fracture toughnessof 5% or greater, a yield strength of 8% or greater than a similarlysized 7075 product and having an exfoliation resistance of EB or better.